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DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il)
Reynolds number: 50,000
Max Cl/Cd: 34.3 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du84132v-il-50000-n5.txt
Download as CSV file: xf-du84132v-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4202   0.09521   0.08780  -0.0544   1.0000   0.0655
  -9.750  -0.4251   0.09176   0.08442  -0.0544   1.0000   0.0651
  -9.500  -0.4340   0.08787   0.08061  -0.0548   1.0000   0.0645
  -9.250  -0.4492   0.08340   0.07622  -0.0556   1.0000   0.0638
  -9.000  -0.4728   0.07917   0.07207  -0.0558   1.0000   0.0632
  -8.750  -0.5032   0.07580   0.06877  -0.0545   1.0000   0.0626
  -8.500  -0.5336   0.07250   0.06549  -0.0529   1.0000   0.0621
  -8.250  -0.5580   0.06890   0.06183  -0.0516   1.0000   0.0615
  -8.000  -0.5772   0.06522   0.05802  -0.0503   1.0000   0.0610
  -7.750  -0.5909   0.06146   0.05406  -0.0492   1.0000   0.0606
  -7.500  -0.5976   0.05789   0.05022  -0.0482   1.0000   0.0601
  -7.250  -0.5987   0.05447   0.04649  -0.0474   1.0000   0.0598
  -7.000  -0.5947   0.05127   0.04294  -0.0467   1.0000   0.0596
  -6.750  -0.5840   0.04827   0.03955  -0.0466   0.9992   0.0596
  -6.500  -0.5545   0.04505   0.03584  -0.0496   0.9932   0.0598
  -6.250  -0.5247   0.04239   0.03273  -0.0519   0.9870   0.0602
  -6.000  -0.4922   0.04013   0.03005  -0.0541   0.9814   0.0609
  -5.750  -0.4623   0.03825   0.02783  -0.0554   0.9751   0.0617
  -5.500  -0.4291   0.03664   0.02589  -0.0571   0.9693   0.0632
  -5.250  -0.3974   0.03532   0.02423  -0.0582   0.9629   0.0655
  -5.000  -0.3662   0.03417   0.02309  -0.0594   0.9563   0.0685
  -4.750  -0.3331   0.03319   0.02200  -0.0606   0.9502   0.0721
  -4.500  -0.3040   0.03232   0.02095  -0.0608   0.9426   0.0752
  -4.250  -0.2698   0.03140   0.02000  -0.0621   0.9372   0.0796
  -4.000  -0.2451   0.03063   0.01915  -0.0618   0.9288   0.0857
  -3.750  -0.2127   0.02974   0.01829  -0.0632   0.9230   0.0984
  -3.500  -0.1871   0.02888   0.01762  -0.0635   0.9153   0.1197
  -3.250  -0.1577   0.02757   0.01697  -0.0651   0.9088   0.2003
  -3.000  -0.1309   0.02618   0.01663  -0.0662   0.9028   0.3862
  -2.750  -0.1121   0.02580   0.01684  -0.0642   0.8946   0.5053
  -2.500  -0.0960   0.02639   0.01803  -0.0589   0.8886   0.6262
  -2.250  -0.0814   0.02703   0.01857  -0.0557   0.8786   0.7011
  -2.000  -0.0539   0.02759   0.01891  -0.0543   0.8728   0.7522
  -1.750  -0.0415   0.02793   0.01912  -0.0508   0.8626   0.7849
  -1.500  -0.0168   0.02798   0.01901  -0.0490   0.8569   0.8164
  -1.250  -0.0057   0.02798   0.01892  -0.0453   0.8469   0.8415
  -1.000   0.0221   0.02778   0.01856  -0.0444   0.8414   0.8638
  -0.750   0.0377   0.02773   0.01841  -0.0419   0.8314   0.8842
  -0.500   0.0729   0.02752   0.01807  -0.0424   0.8260   0.9072
  -0.250   0.1055   0.02754   0.01798  -0.0432   0.8168   0.9290
   0.000   0.1590   0.02741   0.01769  -0.0478   0.8114   0.9437
   0.250   0.1980   0.02743   0.01759  -0.0504   0.8019   0.9543
   0.750   0.2971   0.02727   0.01720  -0.0590   0.7865   0.9735
   1.000   0.3571   0.02707   0.01691  -0.0650   0.7810   0.9839
   1.250   0.3995   0.02708   0.01687  -0.0682   0.7711   0.9986
   1.500   0.4300   0.02684   0.01656  -0.0687   0.7624   1.0000
   1.750   0.4596   0.02649   0.01616  -0.0688   0.7529   1.0000
   2.000   0.4728   0.02645   0.01609  -0.0664   0.7404   1.0000
   2.250   0.4859   0.02643   0.01604  -0.0640   0.7277   1.0000
   2.500   0.5056   0.02637   0.01594  -0.0626   0.7164   1.0000
   2.750   0.5329   0.02623   0.01577  -0.0624   0.7066   1.0000
   3.000   0.5649   0.02601   0.01554  -0.0628   0.6974   1.0000
   3.250   0.5817   0.02624   0.01577  -0.0613   0.6846   1.0000
   3.500   0.6043   0.02639   0.01593  -0.0606   0.6731   1.0000
   3.750   0.6316   0.02647   0.01603  -0.0606   0.6626   1.0000
   4.000   0.6694   0.02624   0.01579  -0.0619   0.6539   1.0000
   4.250   0.6916   0.02648   0.01607  -0.0611   0.6407   1.0000
   4.500   0.7169   0.02664   0.01628  -0.0608   0.6277   1.0000
   4.750   0.7443   0.02678   0.01645  -0.0607   0.6149   1.0000
   5.000   0.7704   0.02699   0.01671  -0.0605   0.6017   1.0000
   5.250   0.7972   0.02722   0.01699  -0.0604   0.5883   1.0000
   5.500   0.8278   0.02731   0.01712  -0.0607   0.5755   1.0000
   5.750   0.8623   0.02726   0.01708  -0.0615   0.5626   1.0000
   6.000   0.8885   0.02752   0.01739  -0.0612   0.5473   1.0000
   6.250   0.9120   0.02790   0.01781  -0.0606   0.5314   1.0000
   6.500   0.9363   0.02825   0.01820  -0.0601   0.5157   1.0000
   6.750   0.9605   0.02861   0.01862  -0.0596   0.5000   1.0000
   7.000   0.9822   0.02907   0.01913  -0.0587   0.4839   1.0000
   7.250   1.0002   0.02963   0.01974  -0.0574   0.4671   1.0000
   7.500   1.0183   0.03006   0.02021  -0.0560   0.4500   1.0000
   7.750   1.0396   0.03031   0.02044  -0.0549   0.4335   1.0000
   8.000   1.0542   0.03090   0.02105  -0.0531   0.4165   1.0000
   8.250   1.0710   0.03150   0.02167  -0.0517   0.4009   1.0000
   8.500   1.0925   0.03200   0.02215  -0.0508   0.3864   1.0000
   8.750   1.1081   0.03280   0.02300  -0.0494   0.3710   1.0000
   9.000   1.1209   0.03373   0.02400  -0.0477   0.3556   1.0000
   9.250   1.1325   0.03473   0.02510  -0.0460   0.3405   1.0000
   9.500   1.1431   0.03577   0.02623  -0.0442   0.3254   1.0000
   9.750   1.1536   0.03685   0.02736  -0.0425   0.3104   1.0000
  10.000   1.1634   0.03801   0.02861  -0.0408   0.2955   1.0000
  10.250   1.1703   0.03937   0.03003  -0.0390   0.2799   1.0000
  10.500   1.1758   0.04082   0.03154  -0.0372   0.2640   1.0000
  10.750   1.1804   0.04241   0.03315  -0.0355   0.2483   1.0000
  11.000   1.1820   0.04429   0.03509  -0.0339   0.2320   1.0000
  11.250   1.1823   0.04635   0.03723  -0.0324   0.2162   1.0000
  11.500   1.1830   0.04848   0.03940  -0.0312   0.2021   1.0000
  11.750   1.1848   0.05065   0.04157  -0.0302   0.1900   1.0000
  12.000   1.1884   0.05278   0.04365  -0.0293   0.1800   1.0000
  12.250   1.1906   0.05534   0.04635  -0.0287   0.1696   1.0000
  12.500   1.1940   0.05776   0.04880  -0.0281   0.1613   1.0000
  12.750   1.1986   0.06015   0.05122  -0.0277   0.1539   1.0000
  13.000   1.2035   0.06266   0.05380  -0.0272   0.1470   1.0000
  13.250   1.2101   0.06497   0.05610  -0.0268   0.1401   1.0000
  13.500   1.2124   0.06797   0.05925  -0.0266   0.1335   1.0000
  13.750   1.2145   0.07090   0.06226  -0.0266   0.1267   1.0000
  14.000   1.2118   0.07457   0.06611  -0.0269   0.1209   1.0000
  14.250   1.2060   0.07862   0.07035  -0.0276   0.1154   1.0000
  14.500   1.2044   0.08207   0.07385  -0.0282   0.1100   1.0000
  14.750   1.1931   0.08723   0.07927  -0.0298   0.1056   1.0000
  15.000   1.1931   0.09057   0.08264  -0.0306   0.1009   1.0000
  15.250   1.1897   0.09480   0.08699  -0.0318   0.0972   1.0000
  15.500   1.1733   0.10152   0.09403  -0.0346   0.0945   1.0000
  15.750   1.1575   0.10835   0.10108  -0.0378   0.0920   1.0000
  16.000   1.1488   0.11400   0.10687  -0.0403   0.0893   1.0000
  16.250   1.1647   0.11487   0.10763  -0.0397   0.0855   1.0000
  16.500   1.1284   0.12654   0.11963  -0.0465   0.0848   1.0000
  16.750   1.0682   0.14549   0.13879  -0.0583   0.0848   1.0000
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